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WO1999019674A1 - Chambre de combustion a debit de carburant pouvant etre regule de maniere independante selon les differents etages - Google Patents

Chambre de combustion a debit de carburant pouvant etre regule de maniere independante selon les differents etages Download PDF

Info

Publication number
WO1999019674A1
WO1999019674A1 PCT/US1998/021335 US9821335W WO9919674A1 WO 1999019674 A1 WO1999019674 A1 WO 1999019674A1 US 9821335 W US9821335 W US 9821335W WO 9919674 A1 WO9919674 A1 WO 9919674A1
Authority
WO
WIPO (PCT)
Prior art keywords
fuel
members
flow
passage
combustor according
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/US1998/021335
Other languages
English (en)
Inventor
David Marchant Parker
Graydon Lane Whidden
Wendel Zolyomi
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens Energy Inc
Original Assignee
Siemens Westinghouse Power Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens Westinghouse Power Corp filed Critical Siemens Westinghouse Power Corp
Priority to AU12699/99A priority Critical patent/AU1269999A/en
Priority to KR1020007003901A priority patent/KR20010024477A/ko
Priority to EP98956100A priority patent/EP1025398A1/fr
Publication of WO1999019674A1 publication Critical patent/WO1999019674A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F02C7/222—Fuel flow conduits, e.g. manifolds
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C6/00—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion
    • F23C6/04—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection
    • F23C6/045—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection with staged combustion in a single enclosure
    • F23C6/047—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection with staged combustion in a single enclosure with fuel supply in stages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones

Definitions

  • the present invention relates to a combustor for burning fuel in compressed air. More specifically, the present invention relates to a combustor in which fuel is introduced by fuel tubes into two pre-mixing passages.
  • fuel is burned in compressed air, produced by a compressor, in one or more combustors.
  • combustors had a primary combustion zone in which an approximately stoichiometric mixture of fuel and air was formed and burned in a diffusion type combustion process. Additional air was introduced into the combustor downstream of the primary combustion zone.
  • the overall fuel/air ratio was considerably less than stoichiometric, the fuel/air mixture was readily ignited at start-up and good flame stability was achieved over a wide range of firing temperatures due to the locally richer nature of the fuel/air mixture in the primary combustion zone.
  • a combustor such as that suitable for use in a gas turbine, in which the flow of fuel to multiple pre-mixing passages can be individually controlled.
  • a combustor for combusting a flow of fuel in a flow of oxygen bearing fluid, such as compressed air.
  • the combustor comprises (i) first and second passages for mixing first and second portions of the fuel flow in first and second portions of the flow of oxygen bearing fluid, respectively, and (ii) means for introducing the fuel flow into first and second portions of the flow of oxygen bearing fluid.
  • the first passage has an inlet for receiving the first portion of the oxygen bearing fluid flow
  • the second passage has an inlet for receiving the second portion of the oxygen bearing fluid flow.
  • the fuel introducing means comprises two members, a first member having means for introducing the first portion of the fuel flow into the first passage and a second member having means for introducing the second portion of the fuel flow into the second passage.
  • the second member of the fuel introducing means extends through the first member of the fuel introducing means.
  • the combustor further comprises means for individually regulating the flow rate of the first portion of the fuel flow introduced by the first portion of the fuel introducing means and the flow rate of the second portion of the fuel flow introduced by the second portion of the fuel introducing means.
  • the fuel flow introducing means comprises a plurality of fuel introducing assemblies, each of which comprises first and second members. The first members are dispersed about the first passage, while the second members are dispersed about the second passage. A first chamber distributes the first portion of the fuel flow to the plurality of first members and a second chamber distributes the second portion of the fuel flow to the plurality of second members. The flow of fuel to the two chambers can be individually regulated by control valves.
  • Figure 3 is a longitudinal cross-section through the primary gas fuel tube assembly shown in Figure 2.
  • Figure 4 is an isometric view of the air inlet portion of the combustor primary section shown in Figure 2, with the flow guide shown in phantom for clarity.
  • Figure 5 is a detailed view of the primary gas fuel manifold shown in Figure 3.
  • Figure 1 the combustion section of a gas turbine.
  • the gas turbine is comprised of a compressor 2 that is driven by a turbine 6 via a shaft 26.
  • Ambient air is drawn into the compressor 2 and compressed.
  • the compressed air 8 produced by the compressor 2 is directed to a combustion system that includes one or more combustors 4 disposed within a chamber 7 formed by a cylindrical shell 22.
  • gaseous or liquid fuel is burned in the compressed air 8, thereby producing a hot compressed gas 20.
  • Each combustor has a primary zone 30 and a secondary zone 32.
  • the hot compressed gas 20 produced by the combustor 4 is directed to the turbine 6 by a duct 5 where it is expanded, thereby producing shaft horsepower for driving the compressor 2, as well as a load, such as an electric generator.
  • the expanded gas produced by the turbine 6 is exhausted, either to the atmosphere directly or, in a combined cycle plant, to a heat recovery steam generator and then to atmosphere.
  • the primary zone 30 of the combustor 4 is supported by a support plate 28.
  • the support plate 28 is attached to a cylinder 13 that extends from the shell 22 and encloses the primary zone 30.
  • the secondary zone 32 is supported by arms (not shown) extending from the support plate 28. Separately supporting the primary and secondary zones 30 and 32 reduces thermal stresses due to differential thermal expansion.
  • a primary combustion zone 35 in which a lean mixture of fuel and air is burned, is located within the primary zone 30 of the combustor 4. Specifically, the primary combustion zone 35 is enclosed by a cylindrical inner liner 44.
  • the inner liner 44 is encircled by a cylindrical middle liner 42 that is, in turn, encircled by a cylindrical outer liner 40.
  • the liners 40, 42 and 44 are concentrically arranged so that an annular secondary pre-mixing passage 50 is formed between the middle and outer liners 42 and 44, respectively.
  • Secondary gas fuel is directed from a manifold 38 to an annular secondary gas fuel ring 36 that distributes gaseous fuel around the inlet to passage 50 into secondary combustion air
  • the fuel/ air mixture produced by the secondary pre-mixing passage 50 is directed to a secondary combustion zone (not shown).
  • a fuel nozzle 18 is centrally disposed within the primary zone 30 and is supplied with oil fuel 14.
  • the fuel nozzle 18 may be supplied with gaseous fuel and/ or water for additional NOx control.
  • Compressed air from the compressor 2 is introduced into the primary combustion zone 35 by a primary air inlet formed in the front end of the primary zone 30.
  • the primary air inlet is formed by first and second primary pre-mixing passages 48 and 49 that divide the incoming air into two streams 8' and 8".
  • the first primary pre-mixing passage 48 has an upstream radial portion and a downstream axial portion.
  • the upstream portion of the first passage 48 is formed between a radially extending circular plate 60 and the radially extending portion of a flow guide 46.
  • the downstream portion is formed between the flow guide 46 and the outer sleeve 34 of the fuel nozzle 18 and is encircled by the second passage 49.
  • the second primary pre-mixing passage 49 also has an upstream radial portion and a downstream axial portion.
  • the upstream portion of second passage 49 is formed between the radially extending portion of the flow guide 46 and a radially extending portion of the inner liner 44.
  • the downstream portion of second passage 49 is formed between the axial portion of the flow guide 46 and an axially extending portion of the inner liner 44.
  • a number of swirl vanes 22 and 24 are distributed around the circumference of the upstream portions of the primary pre- mixing passages 48 and 49.
  • the swirl vanes 22 in the inlet of the first passage 48 impart a counterclockwise (when viewed in the direction of the axial flow) rotation to the air stream 8' .
  • the swirl vanes 24 in the inlet of second passage 49 impart a clockwise rotation to the air stream 8".
  • the swirl imparted by the vanes 22 and 24 to the air streams 8' and 8" ensures good mixing between fuel 16' and 16" and the air, thereby eliminating locally fuel rich mixtures and the associated high temperatures that increase NOx generation.
  • a number of axially oriented, primary fuel spray tube assemblies, or pegs, 52 are distributed around the circumference of the primary air inlet.
  • the primary fuel tubes 52 serve to introduce fuel 16, which is preferably gaseous, into the first and second primary pre-mixing passages 48 and 49. Consequently, the primary fuel tubes 52 extend through the upstream portions of the both the first and second passages 48 and 49.
  • a primary fuel spray tube assembly 52 is located between each of the swirlers 22 and
  • the primary fuel spray tube assemblies 52 are supplied with fuel 16 by a circumferentially extending tubular manifold 70 disposed within the support plate 28.
  • the manifold 70 forms a hollow cavity that is divided into two chambers 71 and 72 by a circumferentially extending baffle 74.
  • separate fuel supply pipes 62 and 64 supply separate streams of fuel 16" and 16', respectively, to chambers 71 and 72, respectively.
  • a control valve 76 is installed in each of the fuel pipes 62 and 64 so that the flow rate of fuel 16' and 16" can be separately regulated.
  • each primary fuel spray tube 52 is an assembly comprised of two tubular members 53 and 54.
  • Member 53 has two rows of fuel discharge ports 66 spaced along its length.
  • Member 54 also has two rows of fuel discharge ports 68 spaced along its length.
  • member 54, and hence its fuel discharge ports 68 extends only through the first pre- mixing passage 48 so as to supply fuel 16' to only that passage.
  • member 53 extends through both pre-mixing passages 48 and 49, its fuel discharge ports 66 are located in only the portion that extends through the second pre-mixing passage 49.
  • member 53 supplies fuel 16" to only the second pre-mixing passage 49.
  • the fuel discharge ports 66 and 68 are oriented so as to discharge the fuel circumferentially in the clockwise and counterclockwise directions within the inlets of pre-mixing passage 48 and 49.
  • the proximal end of member 53 is attached, for example by welding, to the manifold baffle 74, through which it extends.
  • the inlet of member 53 is thus in flow communication with the chamber 71 of the fuel manifold 70.
  • the proximal end of member 54 is attached to the outer wall of the circumferentially extending manifold 70, through which it extends.
  • member 53 has a reduced diameter portion 53' that extends through member 54. Consequently, an annular gap is formed between members 53 and 54 that forms a fuel passage 55.
  • Fuel passage 55 is in flow communication with chamber 72 of the manifold 70, thereby supplying fuel 16" to the discharge ports 68.
  • the distal end of member 54 is attached, for example by welding, to member 53 so as to seal the end of the passage 55.
  • the joint along which the members 53 and 54 are joined is disposed within the passage in the vertical flange of the liner 46 through which the fuel tube assembly 52 extends.
  • the configuration of the primary fuel tubes 52 of the current invention has several advantages. First, since the fuel mbe 53 for second pre-mixing passage 49 extends through the fuel tube 54 for the first pre-mixing passage 48, there is minimal obstruction of the flow area of the pre-mixing passages.
  • this arrangement minimizes stresses due to differential thermal expansion. Note that relatively cool fuel 16' and 16" flows over and through, respectively, the reduced diameter portion 53' of member 53, whereas much hotter air 8' flows over member 54, which surrounds the reduced diameter portion 53'. Consequently, member 54 will expand more than the reduced diameter portion 53' of the other member. According to the current invention, this differential growth is accommodated by the flexibility of the baffle 74, which can bend to accommodate growth, thereby reducing thermal stresses on the assembly.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)

Abstract

Chambre de combustion pour une turbine à gaz, dotée d'une tuyère pour carburant centrale et de chemises cylindriques concentriques interne, intermédiaire et externe, la chemise interne enfermant une zone de combustion primaire. Ladite chambre possède un orifice d'entrée d'air qui forme deux passages destinés au mélange préalable de carburant primaire et d'air destiné à être introduit dans la zone de combustion primaire. Chacun des passages de mélange préalable possède une série circonférentielle d'aubes de turbulence. Une pluralité d'ensembles tubes de carburant primaire s'étendent dans les deux passages de mélange préalable, chaque ensemble tubes de carburant primaire étant situé entre une paire d'aubes de turbulence. Chaque ensemble tubes de carburant primaire est composé de deux éléments tubulaires. Le premier élément approvisionne en carburant le premier passage de mélange préalable, tandis que le second élément, qui s'étend dans le premier élément, approvisionne en carburant le second passage de mélange préalable. Un collecteur de carburant annulaire est divisé en première et seconde chambres par un déflecteur à extension circonférentielle. L'extrémité proximale du premier élément est attachée au collecteur lui-même, tandis que l'extrémité proximale du second élément est attachée au déflecteur. L'extrémité distale du premier élément est attachée directement au second élément autour de son point médian. Les orifices d'entrée des premier et second éléments sont en communication fluidique respectivement avec les première et seconde chambres du collecteur. Des vannes de régulation régulent de manière séparée le flux de carburant entrant dans les deux chambres et, par conséquent, dans les deux éléments des ensembles tubes de carburant, ce qui permet la régulation séparée du flux de carburant vers les premier et second passages de mélange préalable.
PCT/US1998/021335 1997-10-13 1998-10-09 Chambre de combustion a debit de carburant pouvant etre regule de maniere independante selon les differents etages Ceased WO1999019674A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
AU12699/99A AU1269999A (en) 1997-10-13 1998-10-09 Combustor with independently controllable fuel flow to different stages
KR1020007003901A KR20010024477A (ko) 1997-10-13 1998-10-09 독립적으로 제어 가능한 서로 다른 스테이지로의 연료유동을 가진 연소기
EP98956100A EP1025398A1 (fr) 1997-10-13 1998-10-09 Chambre de combustion a debit de carburant pouvant etre regule de maniere independante selon les differents etages

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US08/949,252 1997-10-13
US08/949,252 US5983642A (en) 1997-10-13 1997-10-13 Combustor with two stage primary fuel tube with concentric members and flow regulating

Publications (1)

Publication Number Publication Date
WO1999019674A1 true WO1999019674A1 (fr) 1999-04-22

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US1998/021335 Ceased WO1999019674A1 (fr) 1997-10-13 1998-10-09 Chambre de combustion a debit de carburant pouvant etre regule de maniere independante selon les differents etages

Country Status (7)

Country Link
US (1) US5983642A (fr)
EP (1) EP1025398A1 (fr)
KR (1) KR20010024477A (fr)
AR (1) AR017332A1 (fr)
AU (1) AU1269999A (fr)
TW (1) TW362129B (fr)
WO (1) WO1999019674A1 (fr)

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US5983642A (en) 1999-11-16
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TW362129B (en) 1999-06-21
AR017332A1 (es) 2001-09-05

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